• 专利附录
  • 专利说明
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    • 专利摘要:
    The invention relates to a sealing arrangement for reducing the leakage between components of turbo machines. The seal assembly (10) may include a metallic shim (16), at least a pair of non-metallic end blocks (12A, 12B) and ceramic fibers (14) positioned between the shim (16) and the end blocks (12A, 12B). The insert (16) is mechanically connected to the end blocks (12A, 12B) via several straps (50) so that the metallic insert (16), the non-metallic end blocks (12A, 12B) and the ceramic fibers (14) are connected . The end blocks (12A, 12B) are designed to compensate for misalignment of turbine components by ensuring sealing engagement of the seal assembly (10) with the components. The end blocks (12A, 12B) are made of a ceramic or glass material and the ceramic fibers (14) can be a high-temperature ceramic fiber fabric. The ceramic fibers (14) and / or the end blocks (12A, 12B) protect the metallic shim (16) from reaching potentially harmful temperatures during use of the seal assembly (10), such as use in high temperature turbines with CMC components.
    公开号:CH711014B1
    申请号:CH00495/16
    申请日:2016-04-14
    公开日:2021-03-31
    发明作者:Nandkumar Sarawate Neelesh；Sevincer Edip；Marin Anthony
    申请人:Gen Electric；
    IPC主号:
    专利说明:

    BACKGROUND OF THE INVENTION
    The present application relates generally to seals for reducing leakage and, more particularly, to seals designed to operate within a seal recess to reduce leakage between adjacent stationary components of turbomachinery.
    Leakage of hot combustion gases and / or cooling flows between turbomachine components generally causes a reduced power output and a lower degree of efficiency. For example, hot combustion gases can be trapped within a turbine by providing pressurized compressor air around a hot gas path. Leakage of high pressure cooling streams between adjoining turbine components (such as stator shrouds, vanes and nozzles, inner shell components, and rotor components) into the hot gas path usually results in reduced efficiency and requires an increase in the combustion temperature and a reduction in the engine's gas turbine efficiency to maintain a desired level of performance relative to an environment without such leakage. Turbine efficiency can therefore be improved by reducing or eliminating leakage between turbine components.
    Traditionally, leakage between turbine component junctions has been treated with metal seals positioned in the seal recesses formed between the turbine components, such as stator components. Sealing recesses usually run over the transitions between components, so that metallic seals positioned therein block or otherwise inhibit leakage through the transitions. Avoiding leakage between turbine component transitions with metallic recess seals positioned in seal recesses in the turbine components is made more difficult by the relatively high temperatures that are generated in modern turbo machines. With the introduction of new materials, such as composite ceramic matrix (CMC) turbine components that allow turbines to operate at higher temperatures (e.g., over 1500 degrees Celsius) than traditional turbines, conventional metallic turbine gap seals may be suitable for use in seal recesses inadequate.
    Avoiding leakage between turbine component transitions with metallic seals is made even more difficult by the fact that the seal recesses of turbine components are formed by corresponding recess parts in adjacent components (with a seal positioned therein thereby extending over a transition between components). A misalignment between these adjoining components, such as that resulting from thermal expansion, manufacturing, assembly and / or installation limitations, etc., creates an uneven seal recess contact surface, the design, shape and / or size of which can vary over time. Such non-uniformities on the seal recess contact surface allow leakage through a recess seal positioned in the seal recess when the seal does not bend, deform or otherwise compensate for such non-uniformities. Unfortunately, many conventional metallic shims, which are responsible for such non-uniform seal recess contact surfaces due to the misalignment of adjacent turbine components, cannot adequately withstand increases in turbine operating temperatures.
    Accordingly, it would be desirable to have composite component transition seals of turbomachinery designed for use in typical turbine seal recesses that are resistant to the increasingly higher operating temperatures of turbines and that accommodate non-uniformities in the seal recess contact surface.
    SUMMARY OF THE INVENTION
    In one aspect, the present disclosure provides a seal assembly for positioning in a seal recess formed at least in part by adjacent turbomachine components to seal a gap extending between the components. The seal assembly includes a pair of end blocks, ceramic fibers, and a metallic shim. The pair of end blocks can be ceramic or glass end blocks, each of which has a sealing surface and a bearing surface. The ceramic fibers can overlay at least part of the bearing surfaces of the end blocks. The metallic insert can overlay at least part of the ceramic fibers and have several tabs. The multiple tabs of the metallic shim can be engaged with the end blocks to connect the end blocks, the ceramic fibers, and the metallic shim.
    In some embodiments, the pair of end blocks may abut engaging surfaces thereof to form a joint, and the metallic shim may have at least one tab positioned on a first side of the joint and at least one second tab positioned on a second side of the connection point is positioned which is substantially opposite to the first side of the connection point. In some such embodiments, the junction between the end blocks may extend along the gap between the turbomachine components when the seal assembly is positioned in the seal recess.
    In some embodiments, the pair of end blocks can be in abutment against engagement surfaces of the end blocks that extend along a longitudinal direction of the end blocks and a thickness direction that extends between the sealing surfaces and the bearing surfaces of the end blocks, and the engagement surfaces can be shaped to allowing movement of the end blocks with respect to one another at least along the thickness direction. In some such embodiments, the metallic shim and ceramic fibers may be deformable to permit movement of the end blocks with respect to one another, at least along the thickness direction. In some other such embodiments, the engaging surface of each of the end blocks may have at least a portion extending in the thickness direction along a width direction of the end blocks when extending. In some such embodiments, the engagement surface of each of the end blocks may have a planar surface that extends between the sealing surface and the bearing surface of the respective end block. In some other such embodiments, the engagement surface of one of the end blocks can define a concave shape that extends along the width direction and the other of the end blocks can define a convex shape that extends along the width direction.
    In some embodiments, the end blocks may each have at least one groove configured to receive at least a portion of the metallic shim therein. In some such embodiments, each of the end blocks may have a groove positioned on substantially opposite sides of the end blocks along a longitudinal direction of the end blocks, and the plurality of tabs of the metallic shim may be on substantially opposite sides of a structure formed by the end blocks along a width direction the end blocks must be positioned. In some such embodiments, the grooves of each of the end blocks can be formed on the sealing surface of the end blocks and the plurality of tabs of the metallic shim can extend along a thickness direction that extends between the bearing surface and the sealing surface of the end blocks. In some other embodiments, end blocks may have grooves positioned on substantially opposite sides of a structure formed by the end blocks along a widthwise direction of the end blocks, and recesses positioned on substantially opposite sides of the end blocks along a longitudinal direction of the end blocks Grooves and recesses can be positioned between the bearing surface and the sealing surface of the end blocks. In some such embodiments, the plurality of tabs of the metallic shim may be configured along a thickness direction extending between the bearing surface and the sealing surface of the end blocks such that at least one tab is at least partially positioned within each of the flutes and the recesses.
    In some embodiments, the plurality of tabs can apply a biasing force against the end blocks at least when the seal assembly is at ambient temperature. In some embodiments, the sealing arrangement can be built into the sealing recess and the ceramic fibers can thermally isolate the metallic shim from the sealing recess. In some embodiments, the ceramic fibers can comprise woven metal oxide fibers. In some such embodiments, the metal oxide fibers can be Al2O3 or Al2O3 and SiO2 fibers.
    In a further aspect, the present disclosure provides a turbomachine having a first turbine component, a second turbine component adjoining the first turbine component, and a seal. The first and second turbine components may form at least a portion of a seal recess that extends across a gap between the turbine components. The seal may be positioned within the seal recess of the first and second turbine components and extend across the gap therebetween. The seal can include a pair of end blocks, ceramic fibers, and a metallic shim. The pair of end blocks can be ceramic or glass end blocks, each of which has a sealing surface and a bearing surface. The ceramic fibers can overlay at least part of the bearing surfaces of the end blocks. The metallic insert can overlay at least part of the ceramic fibers and have several tabs. The multiple tabs of the metallic shim can be engaged with the end blocks to connect the end blocks, the ceramic fibers, and the metallic shim.
    In some embodiments, the pair of end blocks may be in abutment along engagement surfaces thereof that extend in a longitudinal direction of the end blocks and a thickness direction extending between the sealing surface and a bearing surface of the end blocks, and the engagement surfaces may be configured to accommodate movement of the end blocks with respect to each other at least along the thickness direction. In some embodiments, the pairs of end blocks may each have at least one groove configured to receive at least a portion of the metallic shim therein.
    These and other objects, features, and advantages of this disclosure will become apparent from the following detailed description of the various aspects of the disclosure when taken in conjunction with the accompanying drawings.
    BRIEF DESCRIPTION OF THE DRAWINGS
    1 is a perspective view of an exemplary seal assembly for use in a turbine seal recess in accordance with the present disclosure;
    Figure 2A is a perspective view of a first end block of the seal assembly of Figure 1;
    Figure 2B is a front view of the first end block of the seal assembly of Figure 1;
    Figure 2C is a side view of the first end block of the seal assembly of Figure 1;
    Figure 2D is an enlarged side view of an end portion of the first end block of the seal assembly of Figure 1;
    Figure 3A is a perspective view of a second end block of the seal assembly of Figure 1;
    Figure 3B is a front view of the second end block of the seal assembly of Figure 1;
    Figure 3C is a side view of the second end block of the seal assembly of Figure 1;
    Figure 4 is a perspective view of an assembly of the first and second end blocks of the seal assembly of Figure 1;
    Figure 5 is a perspective view of an assembly of the first and second end blocks and ceramic cloth of the seal assembly of Figure 1;
    6 is a side cross-sectional view of the seal assembly of FIG. 1 positioned in a seal recess for sealing an exemplary transition between turbine components;
    7 is a perspective view of another exemplary seal assembly for use in a seal recess of a turbine in accordance with the present disclosure;
    Figure 8 is a perspective view of an assembly of the first and second end blocks of the seal assembly of Figure 7;
    Figure 9 is an enlarged perspective view of a portion of the first end block of the seal assembly of Figure 7;
    Figure 10 is an enlarged perspective view of a portion of the second end block of the seal assembly of Figure 7;
    Figure 11 is a cross-sectional view of the first end block of the seal assembly of Figure 7;
    Figure 12A is another cross-sectional view of the first end block of the seal assembly of Figure 7;
    Figure 12B is a cross-sectional view of the second end block of the seal assembly of Figures 7 and 8
    FIG. 13 is a perspective view of an assembly of the first and second end blocks and ceramic cloth of the seal assembly of FIG. 7.
    DETAILED DESCRIPTION OF THE INVENTION
    The articles “a”, “an”, “the” and “said” mean that there is one or more of the elements identified by them. It is intended that the terms “have”, “have” and “have” are comprehensive and mean that there may be additional elements in addition to the elements listed. Examples of operating parameters do not exclude other parameters of the disclosed embodiments. Components, aspects, features, configurations, arrangements, uses, and the like described, illustrated, or otherwise disclosed herein with respect to a particular seal embodiment may equally be applied to any other seal arrangement disclosed herein.
    Composite component transition seals of turbine engines that are designed for use in turbine seal recesses (e.g. composite turbine gap seals), and methods for producing and using the same are designed according to the present disclosure so that they can withstand the relatively high operating temperatures of turbines with CMC Components are resistant or correspond to irregularities on the seal recess contact surface. In particular, the assembled recess seals are designed in such a way that they essentially prevent chemical interaction and essentially limit thermal interaction of metallic components of the assembled recess seals with the hot gas flow / leakage and / or the seal recess itself. Thus, the composite cavity seals contemplated herein enable use in high temperature turbine applications. The composite cavity seals of the present disclosure are designed to, in addition to operating at high temperature, conform to imperfections in the seal cavity contact surface to reduce leakage due to misalignment and / or roughness of the seal cavity surface.
    As shown in Figures 1-6, the exemplary gasket 10 may be a gasket assembly having at least one pair of non-metallic end blocks 12A, 12B, at least one metallic shim 16, and ceramic fibers 14 between the end blocks 12A, 12B and the at least one metallic insert 16 in the direction of thickness T of the insert 10. When used in a seal recess of a turbine engine, the seal 10 can substantially block or seal at least one transition or gap between turbine components and the ceramic fibers 14 (and possibly the end blocks 12A, 12B) can prevent at least the metallic shim 16 from reaching potentially harmful high temperatures ( eg temperatures which lead to silicide formation, thermal creep and / or higher wear of at least the metallic insert 16). In other words, the ceramic fibers 14 (and potentially the end blocks 12A, 12B) allow the seal 10 to have the metallic shim 12 and still be used in high temperature gas turbine applications without affecting the metallic shim 12.
    The at least one pair of end blocks 12A, 12B can be designed so that it engages with the sealing surfaces of a sealing recess formed between at least two turbine components to provide a transition, junction or transition between the components Seal the gap as shown in Fig. 6 and discussed further below. Thus, the end blocks 12A, 12B can be made of a material that can withstand the high temperatures prevailing in a sealing recess of a turbine engine, such as a modern high temperature turbine with CMC components, and can potentially be machined. For example, the end blocks 12A, 12B can be made from or include a ceramic or a glass material. In some embodiments, the end blocks 12A, 12B may be ceramic composite (CMC) end blocks 12A, 12B with fibers and / or a matrix that are stable at temperatures above at least 1800 ° C, such as fibers and / or a matrix of or with alumina , Zirconium dioxide, silicon carbide (SiC) or carbon. In some other embodiments, the end blocks 12A, 12B can be glass end blocks 12A, 12B. In some embodiments, the end blocks 12A, 12B can be made from a crystalline, glass, or glass-ceramic composite. For example, the end blocks 12A, 12B can comprise silicon nitride, silicon carbide, intermetallic compounds such as MAX phase materials (Ti2AlC), and combinations thereof. In some embodiments, the end blocks 12A, 12B can be made from a machinable glass-ceramic material. In some such embodiments, the end blocks 12A, 12B can be made from a borosilicate glass material. For example, in some such embodiments, the end blocks 12A, 12B can be made from a machinable glass-ceramic sold under the Macor® trademark by Corning Inc. of Corning, NY, USA. The end blocks 12A, 12B can each also be substantially effective to substantially prevent the passage of materials therethrough. For example, the end blocks 12A, 12B may be substantially solid or otherwise substantially impermeable to gases and / or liquids and / or solids at pressures and temperatures generated in the turbomachines.
    As shown in FIGS. 2A to 3, each end block 12A, 12B may have a base portion 20, substantially opposite side wall portions 30 extending from the base portion 20 in the thickness direction .T of the gasket 10, and a distal portion 34 extending from each of the side walls 30, include or define. The base part 20 of each end block 12A, 12B can have or define an outer sealing surface or side 22. In some embodiments, the outer sealing surface 22 of each end block 12A, 12B (in a neutral state of the end blocks 12A, 12B) can be substantially planar. As will be explained further below, the outer sealing surface 22 of each end block 12A, 12B can be designed to come into sealing engagement with at least the sealing surfaces of a sealing recess formed by a first and a second turbine component, in order to essentially remove gases, liquids and / or solids to prevent migrating through a gap or joint between the first and second components. Therefore, the sealing surface 22 of each end block 12A, 12B can be shaped, dimensioned and / or otherwise designed so that when the seal 10 is used in a sealing recess of a turbine, the sealing surfaces 22 with at least the corresponding sealing surfaces of the sealing recess of the first and the second second turbine part are sealingly engaged.
    As also shown in FIGS. 2A through 3, the base portion 20 of each end block 12A, 12B may include or define a support surface or side 24. The bearing surface 24 of each end block 12A, 12B may be substantially opposite to the sealing surface 22 thereof. In some embodiments, the bearing surface 24 of each end block 12A, 12B (in a neutral state of the end blocks 12A, 12B) can be substantially planar. As further discussed below, the support surfaces 24 of the end blocks 12A, 12B can cooperate to support ceramic fibers 14 positioned thereon or above. As such, the support surface 24 of each end block 12A, 12B can be shaped, sized, or otherwise configured to support ceramic fibers 14 thereon or thereover.
    The end blocks 12A, 12B may also have substantially opposed side walls 30 that extend from the base 20 along the thickness T of the seal 10 in a direction that extends at least generally from the sealing surface 22 to the bearing surface 24. Thus, the side walls 30 of the end blocks 12A, 12B can define or have outer or outer surfaces 32 which define the length L of the seal 10 (ie define the boundary of the seal 10 in the direction of the length L), as shown in FIGS . In other words, the side walls 30 of the end blocks 12A, 12B can define or have outer or outer surfaces 32 which define the ends or outer edges of the seal 10 in the longitudinal direction L, as shown in FIGS. 1 and 6. In some embodiments, the side walls 30 can be substantially planar and extend substantially perpendicular to the base part 20. For example, the outer or outer surfaces 32 of the side walls 30 can be oriented essentially perpendicular to the sealing surface 22 and / or to the support surface 24 of the base part 20. In other embodiments, however, the outer or outer surfaces 32 of the side walls 30 may not be planar and / or substantially perpendicular to the sealing surface 22 and / or the bearing surface 24 of the base part 20. Furthermore, the side walls 30 may not be positioned on substantially opposite sides of the base part 20 and / or do not define the length L of the seal 10. For example, the side walls 30 can define the width W of the seal 10.
    The end blocks 12A, 12B may each further include distal portions 34 extending from the side walls 30 that are spaced from the base portion 20 along the thickness direction T of the gasket, as shown in Figures 1-6. The distal portions 34 may extend substantially from the outer sides 32 of the side walls 30 along the length L of the seal 10 (e.g., toward the inner portion of the seal 10). In other words, the distal portions 34 of the end blocks 12A, 12B may extend from the side walls 30 and toward the inner or central portion of the seal 10, such as along the length L of the seal 10. In some embodiments, the distal portions 34 can be substantially planar and extend substantially parallel to the base portion 20. For example, the distal portions 34 may each have or define an outer or outer upper surface 36 that is distal to the base portion 20 and an inner or lower surface that is proximate to the support surface 24 of the base portion 12 of the respective end block 12A, 12B Such surfaces can be oriented flat and essentially parallel to the sealing surface 22 and / or the bearing surface 24 of the base part 20 (and / or essentially perpendicular to the side walls 20). In other embodiments, however, the upper surfaces 36 and / or the lower surfaces of the distal parts 34 may not be planar and / or substantially parallel to the sealing surface 22 and / or to the bearing surface 24 of the base part 20 (and / or substantially perpendicular to the side walls 20 ) be oriented. The outer or outer top surfaces 36 of the distal portions 34 of the end blocks 12A, 12B may define the top or top of the gasket 10 in the direction of thickness T, as shown in FIGS. Therefore, the distance between the outer or outer upper surfaces 36 and the sealing surfaces 22 of the end blocks 12A, 12B can define or determine the thickness T of the seal 10, as shown in FIGS. 1 and 6.
    As shown in FIGS. 1 through 6, the distal portions 34 can extend from the side walls 30 and toward the inner or central portion of the seal 10 substantially along the base portion 20. Thus, the base portion 20, sidewall positions 30, and distal portions 34 can form a C-shape as shown in Figures 2C, 2D and 3C (e.g., when viewed along the width W direction). The distal portions 34 may end before they join or reach one another, as shown in FIGS. 1-6. It is therefore possible that at least an inboard or central part of the base part 20 of each end block 12A, 12B is not covered or enclosed by the distal parts 34. At least an inboard or central portion of the bearing surface 24 (e.g., along the length L) of each end block 12A, 12B can thereby be exposed or "open" in the direction of the thickness T of the seal 10.
    The inwardly turned C-shape formed by the inner or inner surfaces of the sidewall positions 30 and the distal portions 34 and the bearing surface 24 of the base portion 20 of each end block 12A, 12B can form a groove, recess, groove or the like 40 which is accessible from an interior (e.g. length L) of the seal 10, as shown in FIGS. The end blocks 12A, 12B can be configured so that the flutes 40 extend the entire width W of the end blocks 12A, 12B. In some embodiments, the flutes 40 may be positioned or disposed on substantially opposite sides of the end blocks 12A, 12B, such as opposite ends of the end blocks 12A, 12B along the length L direction.
    The end blocks 12A, 12B can be configured to fit together in an abutment relationship and form a structure that supports the ceramic fibers 14 and metallic shim 16 to form the seal assembly 10, as in FIGS to 6 shown. As shown in FIG. 4, the end blocks 12A, 12B may be designed or arranged to abut and abut one another along the direction of the width W and along the direction of the length L and the thickness T (in a neutral state of the Seal 10) are essentially aligned. In some embodiments, the bearing surfaces 24 of the end blocks 12A, 12B can be planar, and when the end blocks 12A, 12B are connected, engaged, or abutted (and in a neutral state), the bearing surfaces 24 can be coplanar about a two-part planar surface for supporting the ceramic fibers 14 and the metallic shim 16 thereon, as shown in Figs. Further, the end blocks 12A, 12B can be configured so that when connected, engaged, or abutted (and in a neutral state), the flutes 40 at respective ends or portions of the end blocks 12A, 12B mate and are substantially aligned cooperate. When the end blocks 12A, 12B are connected or abutted, outer lateral sides or side surfaces 38 of the end blocks 12A, 12B along the direction of width W may define or define the outer lateral sides or surfaces of the structure formed by the end blocks 12A, 12B. As will be further discussed below, the shim 16 may engage and / or couple the outer lateral sides of the end blocks 12A, 12B to at least partially interconnect or secure the end blocks 12A, 12B together. The outer lateral sides or surfaces 38 of the end blocks 12A, 12B may be formed or defined by the base portion 20, the side wall portions 30 and the distal portions 34, as shown in Figures 2C and 3C.
    As shown in Figures 1-5, the end blocks 12A, 12B may have or define internal engagement surfaces 26 that engage or abut one another and form a joint or seam 18 therebetween when the end blocks 12A, 12B are connected or in abutment (and in a neutral state) and form the seal 10. In some embodiments, the engagement surfaces 26 may extend through the thickness T of the end blocks 12A, 12B such that engagement surfaces 26 are formed or defined by the base portion 20, the side wall portions 30, and the distal portions 34, as shown in FIGS. 2C and 3C see. The engagement surfaces 26 may be designed to allow the end blocks 12A, 12B to be moved with respect to one another while maintaining contact or engagement between them, so that the gasket 10 may cause gasket recess alignment errors or other situations that may cause misalignment of gasket relief surfaces (e.g., alignment errors along the direction of the thickness T and / or the width W), equalizes or conforms to them while preventing an increase in leakage across the seal 10. In some embodiments, the engagement surfaces 26 of the end blocks 12A, 12B can be configured such that the junction or seam 18 therebetween substantially corresponds to a gap or transition between turbine components that form a sealing recess for the seal 10 to allow or compensate for movement of the components such as movement in the direction of thickness T. Further, to enable contact or engagement of the end blocks 12A, 12B along the length L of the end blocks 12A, 12B, the shape, size, orientation, or the like of the engagement surfaces 26 may be substantially the same or be mimicked (e.g. being a mirror image).
    In some embodiments, the engagement surfaces 26 of the end blocks 12A, 12B can be planar and angled in their course along the thickness direction T. For example, as shown in FIGS. 2B and 3B, the engaging surfaces 26 of the end blocks 12A, 12B may be planar and angled along the thickness direction T along the width W direction. In such an embodiment, the engagement surface 26 of a first end block 12A can be used to enable movement between the end blocks 12A, 12B while maintaining contact, abutment, or engagement of the engagement surfaces 26 as they extend in the thickness direction T from the engagement surface or side 22 to the top surface or top 36 may be angled towards the second end block 12B, while the second end block 12B may, conversely, be angled away from the first end block 12A in its course in the thickness direction T from the sealing surface or side 22 to the top surface or top 36. Thus, the engaging surfaces 26 of the end blocks 12A, 12B can allow movement or displacement (e.g. sliding movement) between the end blocks 12A, 12B in the width direction that causes or results in a relative displacement of the end blocks 12A, 12B in the direction of the thickness T (and also the allows relative displacement along the longitudinal direction L) while their abutment or their engagement with each other is maintained. As will be further explained below, other geometries or configurations of the engagement surfaces 26 of the end blocks 12A, 12B can potentially inhibit movement between end blocks 12A, 12B (e.g. along the direction of thickness T, width W and / or length L) Make preservation of their system or their intervention possible.
    With the end blocks 12A, 12B engaged, as shown in FIG. 4, the ceramic fibers 14 may be positioned on or over the bearing surfaces 24, as shown in FIG. As noted above, when the end blocks 12A, 12B are adjacent or in engagement or abutment with one another, the support surfaces 24 may cooperate to form a platform, surface (s) or a support mechanism for laying the ceramic fibers 14 thereon or above. In some embodiments, the ceramic fibers 14 may include at least one layer of ceramic fibers or fabric that substantially covers or overlays the bearing surfaces 24 of the end blocks 12A, 12B. For example, the at least one layer of ceramic fibers 14 may be positioned on or above the bearing surfaces 24 (e.g., in abutment therewith) and extend into the grooves 400 of the blocks 12A, 12B, as shown in FIG. In such embodiments, the end blocks 12A, 12B and / or ceramic fibers 14 may be configured such that the ceramic fibers 14 only fill or occupy a portion of the grooves 40 in the direction of the thickness T. In alternative embodiments (not shown), the ceramic fibers 14 may not substantially cover or overlap the bearing surfaces 24 and / or may be positioned in at least one groove 40. The ceramic fibers 14 can be relatively flexible or deformable so that the ceramic fibers 14 do not prevent the relative movement of the end blocks 12A, 12B. In other words, the ceramic fibers 14 can be designed to accommodate movement of the end blocks 12A, 12B with respect to one another, such as in the direction of thickness T, in response to misalignment or a "rough" surface profile of a gasket recess in which the gasket 10 is to be Use comes to allow.
    The ceramic fibers 14 may preferably act as a thermal barrier to the metallic shim 16 positioned over or on the ceramic fibers 14. In other words, the ceramic fibers 14 are preferably designed to reduce the thermal conductivity of the sealing recess receiving the seal 10 to the metallic shim 16 (such as, for example, of the turbine components that form the sealing recess and / or a flow through the gap or transition between the components and on the seal 10 acting hot flow). As will be further explained below, the seal 10 can be used in a seal recess and can be oriented such that the sealing surface 22 of the end blocks 12A, 12B is positioned adjacent to or interacts with a flow or material (e.g. a combustion air flow) that is or that is hotter than a flow or material (for example cooling air flow) that is positioned adjacent to the outer surface 48 of the metallic insert 16 or interacts with it. As such, the ceramic fibers 14 (potentially together with the end blocks 12A, 12B) can cause the metallic shim 16 to reach (or at least reduce the likelihood of) potentially harmful high temperatures (e.g., temperatures that lead to silicide formation, thermal creep and / or higher wear of at least the metallic insert 16). In other words, the ceramic fibers 14 (and potentially the end blocks 12A, 12B) are preferably designed so that the seal 10 has the metallic shim 12 and is used in high temperature gas turbine applications, such as turbines with CMC components, without affecting the metallic shim 18 can be.
    Thus, the ceramic fibers 14 can be any ceramic fiber material that thermally insulates the metallic shim 16 or otherwise acts as a thermal barrier to it. In some embodiments, the ceramic fibers 14 (or the ceramic fibers 14 and the end blocks 12A, 12B) are designed to prevent the metallic shim 16 from exceeding 1800 degrees Fahrenheit (982.2 ° C) when the seal is in a turbine engine, such as a machine with CMC components. In some embodiments, the ceramic fibers 14 (or the ceramic fibers 14 and the end blocks 12A, 12B) are designed to prevent the metallic shim 16 from reaching (or at least the probability of) about 1500 degrees Fahrenheit (815.6 ° C), when the seal 10 is used in a turbine engine, such as a turbine with CMC components.
    The ceramic fibers 14 may be made from metal oxide fibers that have been woven or otherwise made into a ceramic textile such as a fabric, cloth, tape or cover. In some embodiments, the ceramic fibers 14 can be made from fibers of or with Al2O3 or Al2O3 and SiO2. For example, the ceramic fibers can be at least about 99% by weight Al2O3 or about 85% by weight Al2O3 and about 15% by weight SiO2. In some embodiments, the ceramic fibers 14 can be made from fibers that have a crystalline or crystal structure based on alpha-Al2O3 or alpha-Al2O3 and mullite. In some embodiments, the ceramic fibers 14 may be at least one layer of woven ceramic fibers, such as Nextel ™ ceramic textiles, fabrics, or fibers sold by 3M ™. In some such embodiments, the ceramic fibers can be 143M ™ Nextel ™ 610 Ceramic Fiber or 3M ™ Nextel ™ 720 Ceramic Fiber.
    As discussed above, the gasket 10 may include glass end blocks 12A, 12B in addition to the protection afforded by the ceramic fibers 14 to provide further thermal insulation or shielding from the metallic shim 16 of the gasket 10. Such glass end blocks 12A, 12B can lower the thermal conductivity from the seal recess receiving the seal 10 to the metallic insert 16 compared to that provided by the ceramic fibers 14 alone. For example, the glass end blocks 12A, 12B can have a relatively low thermal conductivity (e.g. compared to ceramic (e.g. CMC) end blocks 12A, 12B) which, together with the ceramic fibers 14, causes the thermal conductivity to the metallic seal 16 to be reduced in order to prevent the metallic shim 16 will reach (or at least reduce the likelihood of) potentially detrimental high temperatures during use of the seal 10 in turbomachinery. Glass end blocks 12A, 12B can also become relatively soft, deformable, or resilient at temperatures encountered in the seal recesses of turbo machines. In some such embodiments, the glass end blocks 12A, 12B can be designed to deform (e.g., due to the temperature and pressure generated / experienced in the seal recesses of turbo machinery) and to conform to any misalignment or roughness profile in a seal recess to increase the Prevent leakage through the seal 10.
    The sealing arrangement 10 can have at least one insert 16 which essentially covers or overlays the ceramic fibers 14 and / or the bearing surfaces 24 of the end blocks 12A, 12B. For example, the at least one shim 16 may be positioned (e.g., in abutment therewith) on or over the ceramic fibers 14 (and over the bearing surfaces 24) and extend into the grooves 40 of the blocks 12A, 12B, as shown in FIG. In such embodiments, the end blocks 12A, 12B and / or the ceramic fibers 14 may be configured such that the insert 16 and the ceramic fibers 14 substantially fill or fill in the grooves 40 in the direction of the thickness T. In some embodiments, the grooves 40 can exert a compressive force on the portion of the insert 16 (and potentially the ceramic fibers 14) positioned therein in the direction of the thickness T, at least in a neutral state of the seal 10 (e.g., when the seal 10 is at ambient temperature). Since the shim 10 can be positioned in the grooves 40 of both end blocks 12A, 12B and the grooves 40 can be positioned on substantially opposite sides or portions of the end blocks 12A, 12B (e.g., along sides or portions that extend the length L of the end blocks 12, 12B), the shim 16 and the flutes 40 can effectively couple or secure the end blocks 12A, 12B with respect to one another along at least one direction (e.g., along the direction of length L).
    The at least one metallic insert 16 can have the effect that the passage of substances through it is substantially prevented. For example, the metallic shim 16 may be substantially solid or otherwise impermeable to gases and / or liquids and / or solids at pressures and temperatures generated in turbomachines. The metallic insert 16 can, however, also provide flexibility at pressures and temperatures generated in turbo machines, at least in the direction of the thickness T, in order to compensate for twists and offsets in the seal recess in which the seal 10 is used. For example, the metallic shim 16 can be relatively flexible or malleable so that the metallic shim 16 does not prevent relative movement (e.g., shifting, twisting, bending, etc.) of the end blocks 12A, 12B. In other words, the metallic shim 16 can be configured to flex or deform in response to a misaligned or "rough" surface profile of the gasket recess in which the gasket 10 is used to allow the end blocks to deflect 12A, 12B move with respect to each other at least in the direction of thickness T.
    In one embodiment, at least a portion of the insert 16 overlying the ceramic fibers 14 and / or the bearing surfaces 24 of the end blocks 12A, 12B is a substantially solid metallic element or part. The metallic shim 16 can be a high temperature metal alloy or superalloy. For example, in some embodiments, the shim 16 may be made of stainless steel or a nickel-based alloy (at least in part) such as a nickel-molybdenum-chromium alloy, Haynes 214 or Haynes 214 with an aluminum oxide coating. In some embodiments, the insert 16 may be made from a metal having a melting temperature of at least 1500 degrees Fahrenheit (815.6 ° C), and more preferably at least 1800 degrees Fahrenheit (982.2 ° C). In some embodiments, the insert 16 can be made from a metal with a melting temperature of at least 2200 degrees Fahrenheit (1204 ° C).
    As shown in Fig. 1, the metallic shim 16 may have a sealing portion 46 that substantially covers or overlays the ceramic fibers 14 and / or the bearing surfaces 24 of the end blocks 12A, 12B. In some embodiments, the ceramic fibers 14 may abut, abut, or be beneath the entirety of the sealing portion 46 of the metallic shim 16. In this way, the ceramic fibers 16 can insulate at least the entirety of the sealing part 46 of the metallic insert 16. In other embodiments, at least a portion of the sealing part 46 of the metallic shim 16 can be devoid of the ceramic fibers 14. The shape or configuration of the sealing part 46 of the metallic insert 16 can essentially correspond to that of the bearing surfaces 24 of the end blocks 12A, 12B. For example, the inside, surface, or portion of the sealing member 46 may be engaged with the ceramic fibers 14 and positioned near the bearing surfaces 24 of the end blocks 12A, 12B. The inside of the sealing part 46 can therefore be essentially flat (in a neutral state of the seal 10) and has essentially the same width W and length L as those of the ceramic fibers 14 and / or bearing surfaces 24.
    As is also shown in FIG. 1, a part of an outer side or surface 48 of the sealing part 46 of the metallic insert 16 can be exposed. For example, the exterior or surface of the sealing portion 46 that is not positioned in the grooves 40 may be exposed. The exposed outside or surface 48 of the sealing portion 46 of the metallic shim 16 can be configured to engage or interact with a high pressure cooling air flow passing through at least one gap or junction between at least a first and a second component, the form a seal recess (at least partially) receiving the seal 10, flows. The high pressure cooling air flow acting at least on the exposed outer side or surface 48 of the metallic shim 16 can force the seal (e.g., the sealing sides or surfaces 22 of the end blocks 12A, 12B) against or into contact with the sealing surfaces of the sealing recess squeeze to substantially prevent gases, liquids and / or solids from migrating through the gap or joint. Therefore, the sealing part 46 of the metallic insert 16 can be essentially impermeable to liquids, gases and / or solids at pressures experienced in turbo machines, so that the seal 10 ensures at least a low leakage rate past the seal recess. As described above, the sealing portion 46 of the metallic shim 16 can, however, be flexible in order to allow relative movement between the end blocks 12A, 12B in order to avoid twisting, misalignment or other misalignment of the sealing surfaces of the turbine components, the sealing recess receiving or retaining the seal 10 form, balance.
    The metallic shim 16 can also have a plurality of tabs or projections 50 which extend from the sealing part 46 on at least one side, an edge or a part thereof which is not positioned in a groove 40, as shown in FIG. extend. The tabs 50 may be provided on substantially opposite sides of the insert 16. In the exemplary embodiment shown in FIG. 1, the sides of the sealing portion 46 that define the length L of the shim 16 are positioned in the flutes 40 and the tabs 50 extend from the sides of the sealing portion 46 that extend between the flutes 40 and define the width W of the insert 16. A plurality of tabs 50 may be positioned on each side or portion of the sealing member 46 that has a tab 50.
    The tabs 50 of the metallic shim 16 may be configured to hold, connect, fasten, abut, or in abut the end blocks 12A, 12B in at least one direction, such as along the direction of width W To be engaging. Further, the tabs 50 can couple or attach the shim 16 and ceramic fibers 14 to the end blocks. For example, the tabs 50 may be angled or offset from the sealing member 46 in the thickness direction T so that they extend over or beyond the outer edges or sides of the ceramic fibers 14 and the end blocks 12A, 12B. As shown in FIG. 1, the tabs 50 may extend away from the outside or surface 48 of the sealing member 46 and toward the sealing side or surface 22 of the end blocks 12A, 12B so that the tabs 50 extend over the outer lateral sides or Side surfaces of the ceramic fibers 14 and the outer lateral sides or side surfaces 38 of the end blocks 12A, 12B (e.g., along the length L of the gasket 10) extend or extend beyond them. The tabs 50 of the metallic shim 16 and the grooves 40 of the end blocks 12A, 12B may cooperate to hold the end blocks 12A, 12B, the ceramic fibers 14 and the metallic shim 16 together along the length L, width W and thickness T directions, respectively to connect, fasten or engage. As mentioned above, however, the metallic shim 16 is relatively flexible and the joint 18 extending between the end blocks 12A, 12B is designed to provide or permit movement of the end blocks 12A, 12B in at least the direction of thickness T, so that the seal 10 may maintain sealing engagement with a sealing recess of a turbomachine that is (or will be) offset or has a "rough" profile.
    The metallic insert 16 and the ceramic or glass end blocks 12A, 12B can have different coefficients of thermal expansion (hereinafter CTE). As a result, the metallic shim 16 may expand or enlarge more than the ceramic or glass end blocks 12A, 12B, although the metallic shim 16 may be cooler than the ceramic or glass end blocks 12A, 12B during use of the seal 10 in a seal recess of a turbomachine. In order to compensate for the potential expansion of the metallic shim 16 with respect to the ceramic or glass end blocks 12A, 12B, the tabs 50 can, when at least the metallic shim 16 is heated, such as when heated to at least about an operating temperature of the turbomachine, adjacent to the or positioned along the sides or surfaces of the end blocks 12A, 12B (e.g., deformed so that they are offset or angled with respect to the sealing portion 46 and on or adjacent to the lateral outer sides or surfaces 38 of the end blocks 12A, 12B) . For example, the gasket 10 can be heated to at least 1500 degrees Fahrenheit or at least 1800 degrees Fahrenheit and the tabs 50 can be deformed or positioned on or adjacent to the sides or surfaces of the end blocks 12A, 12B. Since the tabs 50 can be deformed or positioned in a heated state of the metallic shim 16 and the tabs 50 can be positioned on substantially opposite sides of the seal 10, the tabs 50 can be preloaded or preloaded at ambient temperature so that they apply a compressive force exercise the end blocks 12A, 12B. In some embodiments, the tabs 50 may be preloaded so that they are configured to apply a load or force, such as a compressive force, to the end blocks 12A, 12B at ambient temperature and at an operating temperature of the seal 10 (i.e., an operating temperature of a turbine). It should be noted that the load or force exerted by the tabs 50 against the end blocks 12A, 12B may be greater at ambient temperature than at the operating temperature.
    The components of the seal 10 may include one or more protective coatings (not shown) that may be applied or positioned over or on a surface thereof or a portion thereof. For example, at least a portion of the metallic shim 16, such as an exterior or exposed surface thereof, may have at least one protective coating or layer. The protective coating (s) of the metallic insert 16 can be designed in such a way that they can essentially prevent or delay the oxidation of the metallic insert 10. In some embodiments, the protective coating (s) of the metallic shim 16 may comprise or substantially comprise an oxide, such as chromium oxide or aluminum oxide. In some embodiments, the protective coating (s) of the metallic insert 16 can be designed for thermal insulation of the metallic insert 10. For example, the metallic shim 16 may have a thermal barrier coating (TBC) overlying the metallic shim 16 and designed to further thermally isolate the metallic shim 16 (in addition to the thermal insulation provided by the ceramic fibers 14 and potentially the end blocks 12A, 12B). In some embodiments, the TBC may have multiple layers on the metallic insert 16, such as at least one metallic bonding layer formed on the metallic insert 16, at least one thermally grown oxide (TGO) layer or region formed on or in the bonding layer, and at least one a ceramic cover layer formed or positioned on or above the TGO. In some embodiments, the ceramic topcoat may be composed of yttria stabilized zirconia (YSZ) or rare earth silicate or zirconate. The at least one ceramic cover layer can provide the greatest thermal gradient of the TBC and function to lower the temperature of the layers below.
    In some embodiments, the end blocks 12A, 12B can also have a protective coating. For example, at least a portion of the end blocks 12A, 12B, such as the bearing surfaces 24 and / or the sealing surface 22, may have at least one protective coating or layer. The protective coating (s) of the end blocks 12A, 12B can be designed to substantially prevent or retard volatilization-related shrinkage of the end blocks 12A, 12B and / or to thermally insulate the end blocks 12A, 12B. The end blocks 12A, 12B can therefore have a TBC and / or a reaction protection layer (EBC: Environmental Barrier Coating). For example, the end blocks 12A, 12B may have an ECB overlaying at least a portion thereof to prevent volatilization of the end blocks 12A, 12B and potentially further thermally isolate the metallic shim 16 (in addition to that from the ceramic fibers 14 and thermal insulation potentially provided to the end blocks 12A, 12B). In some embodiments, the EBC may have multiple layers on the end blocks 12A, 12B, such as at least one adhesion promoter layer formed on the end blocks 12A, 12B and at least one cover layer formed or positioned over the at least one adhesion promoter layer. It should be noted that ceramic embodiments of the end blocks 12A, 12B, such as CMC end blocks 12A, 12B, have a protective EBC coating to prevent volatilization when the gasket 10 is used in high temperature and / or humid environments can benefit particularly.
    Figure 6 illustrates a cross-sectional view along width W of the example recess seal assembly 10 positioned in an example seal recess to seal an example transition between turbine components. 6 shows a cross-section along the width W of a portion of an exemplary turbine engine that includes an exemplary first turbine component 142, an adjacent exemplary second turbine component 144, and the seal assembly 10 installed in the seal recess formed by the first and second components 142, 144. The first and second turbine components 142, 144 may be first and second stator components, such as first and second vanes of a first and second stator, respectively. In other embodiments, the first and second components 142, 144 can be any other contiguous turbomachine components, such as stationary or translating and / or rotating (i.e., moving) turbine components. In other words, the seals described herein, such as seal 10, can be designed for, or used with, any number or type of turbomachine components that require a seal to reduce leakage between the components.
    The cross-section of exemplary members 142, 144 and seal assembly 10 illustrated in Figure 6 is taken along a width W of the formations, illustrating an example width W and thickness / height T of the formations. It should be noted that the relative width W, thickness T and cross-sectional shape of the structures illustrated in FIG. 6 are exemplary and that the structures can have any other relative width, thickness and cross-sectional shape. Furthermore, the length L of the structures (which extends perpendicular to the drawing in FIG. 6) can be any desired length and the shape and configuration of the structures in the direction of the length L can be any desired shape or configuration. It should also be noted that while only two exemplary turbine components 142, 144 forming a seal recess are shown, multiple components can form multiple seal recesses that are in communication with one another. For example, a plurality of turbine components can be arranged extending in the circumferential direction, so that the sealing recesses formed thereby also extend in the circumferential direction and are connected to one another. In such embodiments, the seals according to the present embodiment, such as seal 10, can be designed to span multiple seal recesses in order to seal multiple gaps or transitions and thereby reduce leakage between multiple turbine components.
    As shown in Fig. 6, the first and second turbine components 142, 144, which adjoin each other, be spaced from each other so that a transition, a gap, is between the first and second components 142, 144, which are adjacent or a passage 190 extends. Such a transition 190 may thereby permit flow, such as airflow, between the first and second turbine components 142, 144. In some configurations, the first and second turbine components 142, 144 may be positioned between a first airflow 150, such as a cooling airflow, and a second airflow 160, such as a hot combustion airflow. It should be noted that the term “airflow” is used herein to describe the movement of a material or composition, or combination of materials or compositions, that translates through the transition 190 between the first and second turbine components 142, 144.
    In order to receive a seal spanning the transition 190 and thereby block or otherwise block the transition 190 and the first air flow 150 and the second air flow 160, the first and second components 142, 144, which adjoin one another, can respectively have a sealing recess, as shown in FIG. 6. In the exemplary illustrated embodiment, the first component 142 has a first sealing recess 170 and the second component has a second sealing recess 180. The first and second seal recesses 170, 180 can be of any size, shape, or configuration suitable for receiving a seal therein. For example, as shown in the illustrated exemplary embodiment in FIG. 6, the first and second sealing recesses 170, 180 may be substantially similar to one another and positioned in a mirror image relationship to together define a useful recess or cavity, which extends from within the first component 142 over the transition 190 and into the second component 144. Thus, the pair of first and second seal recesses 170, 180 can cooperate with one another to form a cavity or seal for supporting opposing portions of the seal assembly 10 such that the seal 10 passes through the transition 190 that extends between the adjoining components 142, 144 .
    In some arrangements in which the first and second turbine components 142, 144 are contiguous, the first and second seal recesses 170, 180 can be configured so that they are substantially aligned (eg, in a mirror image or symmetrical Relationship). However, due to manufacturing and assembly limitations and / or variations, as well as thermal expansion, movement, or other factors, the first and second seal recesses 170, 180 may be twisted, twisted, angled, or otherwise misaligned. In other situations, the first and second sealing recesses 170, 180 may remain in a mirror image or symmetrical relationship, but the relative positioning of the first and second sealing recesses 170, 180 may change (such as due to conditions of use, wear and tear, or operating conditions). . The term "misaligned" is used herein to encompass any situation in which seal recesses have changed relative positions or orientations from a nominal or home position or configuration, such as a manufactured or assembled position or configuration.
    With reference to the exemplary first and second seal recesses 170, 180 of the exemplary first and second turbine components 142, 144 and the seal 10 of FIG. 6, the seal 10 is designed to eliminate the misalignment in a misaligned configuration (not shown) balance and maintain the sealing contact of the end blocks 12A, 12B with the first and second sealing recesses 170, 180 to effectively shut off or eliminate the transition 190 extending between the first and second turbine components 142, 144, thereby reduce or prevent the interaction of the first and second airflows 150, 160. More specifically, as shown in FIG. 6, the first and second airflows 150, 160 can interact with the transition 190 such that the first airflow 150 is a “driving” airflow that is directed against the outside or surface 48 of the metallic insert 16 of the seal 10 acts to press the seal side or surfaces 22 of the end blocks 12A, 12B against first side surfaces 135, 145 of the first and second seal recesses 170, 180, respectively. In such situations, the transition 18 formed by the engagement surfaces 26 of the end blocks 12A, 12B and the flexibility or deformability of the ceramic fibers 14 and metallic shim 14 can reduce the relative movement of the end blocks 12A, 12B (e.g. in the direction of thickness T) as a result of the allow the first air stream 150 applied forces (e.g., beyond those applied by the second air stream 160) to accommodate misalignment between the first and second seal recesses 170, 180, but be stiff enough to "fold" or otherwise "dent" into the Withstand transition 190 into it. In other words, in such a situation, the exemplary seal 10 may preferably be flexible enough, but still rigid enough, to permit the sealing engagement of the seal side or surfaces 22 of the end blocks 12A, 12B of the insert 16 with the respective first side surfaces 135, 145 via the To maintain forces of the first air stream 150. For example, the metallic shim 16, the ceramic fibers 14, and the end blocks 12A, 12B can be configured such that the seal 10 can conform to irregularities in the seal recess contact surfaces 135, 145. In addition to being flexible enough to effectively seal the junction 190 in misalignment situations, the exemplary seal 10 may preferably be stiff enough to meet assembly requirements.
    The size of the seal 10 can be any size, but may depend on, or at least be related to, the components 142, 144 in which the seal 10 is installed. The thickness T of the exemplary seal 10 may be less than the thickness T2 of the first and second sealing recesses 170, 180 and thereby the thickness T2 of the useful recess formed by the first and second sealing recesses 170, 180 when the first and second sealing recesses 170, 180 second component 142, 144, which adjoin each other, are assembled. In some embodiments, the thickness T of the exemplary gasket 10 may preferably be within the range of about 0.01 inch (0.25 mm) to about 1/4 inch (6.35 mm), and more preferably within the range of about 0.05 inch ( 1.3mm) to about 0.1 inch (2.5mm). Likewise, the width W of the seal 10 can be smaller than the width W2 of the useful recess formed by the first and second recesses 170, 180 of the first and second components 142, 144 and of the gap 190 between the components 142, 144, if the components 142, 144 are installed adjacent to one another. In some embodiments, the width W of the exemplary seal 10 may preferably be within the range of about 0.125 inches (3.18 mm) to about 0.75 inches (19 mm).
    For example, as shown in the illustrated embodiment in FIG. 6, the seal 10 can be positioned and disposed within the seal recess (ie, the first and second seal recesses 170, 180) such that the first or cooling air flow 150 against the The outer side or surface 48 of the sealing part 46 of the metallic shim 16 (and the upper surfaces 36 of the distal parts 34) and the outer sealing surface 22 of each end block 12A, 12B against the first side surfaces 135, 145 of the first and second sealing recesses 170, 180 to press. Due to the impermeability of the shim 16 and / or the end blocks 12A, 12B (and due to the fact that the end blocks 12A, 12B are in abutment), the seal 10 can thereby prevent the cooling air flow 150 from passing through the gap 190 and into the second or hot combustion air stream 160 migrates. Furthermore, the ceramic fibers 14 (and potentially the end blocks 12A, 12B) protect the metallic shim 16 from the high temperatures of the combustion air stream 160.
    Thus, at least the shape and configuration of the sealing surfaces 22 of the end blocks 12A, 12B of the seal 10 (e.g. the surface that interacts with the exemplary first side surfaces 135, 145 or other sealing surfaces of the exemplary first and second sealing recesses 170, 180) with the shape and configuration of the recesses 142, 144 in which the seal 10 is installed, and the seal can adapt to changes or deviations in the shape and configuration of the recesses 142, 144 in which the seal 10 is installed ( e.g. moving, deforming, bending, etc.). In other words, the seal 10 can be configured to ensure sealing engagement with the first and second seal recesses 170, 180 in which the seal 10 is installed. For example, in the illustrated example in FIG. 6, the sealing surfaces 22 of the end blocks 12A, 12B of the seal 10 can be essentially smooth (e.g. planar) and on the same plane in order to be able to contact the essentially smooth (e.g. planar) and planar first side surfaces 135, 145 of the first and second seal recesses 170, 180 to be substantially abutted or otherwise substantially engaged to leakage of the first airflow 150 between the seal 10 and the first side surfaces 135, 145 of the first and second seal recesses 170, 180 and ultimately to effectively prevent or reduce the second or hot combustion air flow 160 (and also to protect the metallic insert 16 from the high temperatures of the hot combustion air flow 160). In some alternative embodiments (not shown), the shape and configuration of at least the sealing surfaces 22 of the end blocks 12A, 12B of the seal 10 may differ from that of the corresponding sealing surfaces of the first and second sealing recesses 170, 180 (such as those illustrated in FIG. 6, for example first side surfaces 135, 145 of the first and the second sealing recess 170, 180) be shaped or designed differently. If the sealing surfaces of the first and second sealing recesses 170, 180 are misaligned or shifted planar, the flexibility of the metallic shim 16 and ceramic fibers 14 allows the end blocks 12A, 12B to move relative to one another (e.g., at least in the direction of thickness T) to maintain the engagement of the sealing surfaces 22 with the first and second sealing recesses 170, 180 and the engagement surfaces 26 with one another to prevent leakage of the first airflow 150 between the seal 10 and the first side surfaces 135, 145 of the first and second sealing recesses 170 , 180 and ultimately in the second or hot combustion air flow to effectively prevent or reduce.
    7-13 illustrate another exemplary recess seal assembly 110 in accordance with the present disclosure. The exemplary recess seal assembly 110 has some similarities to the exemplary recess seal assembly 10 of FIGS. 1 through 6 described above, and therefore the same reference numerals with a prefixed “1” are used to denote similar aspects or functions and refer to such aspects or functions (and the alternative embodiments of this) related description above applies equally to the exemplary recess seal assembly 110. As shown in FIGS. 7-13, seal assembly 110 differs from seal 10 in terms of the configuration of end blocks 112A, 112B and the engagement of the metallic shim 116 with the end blocks 112A, 112B.
    In the embodiments of FIGS. 7 to 13, the engagement surfaces 126 (see FIGS. 8 to 10, 12A and 12B) of the end blocks 112A, 112B of the seal 110 are not planar. The engaging surfaces 126 of the first and second end blocks 112A, 112B are convex and concave, respectively, in the direction of the width W and configured to fit or nest together as shown in Figs. 8-10, 12A and 12B ( e.g. are essentially mirror image shapes). The engaging surface 126 of the first end block 112A is convex in the width direction so that it defines an apex that is positioned approximately in the middle of the thickness T of the first end block 112A. The engagement surface 116 of the first end block 112A has portions positioned above and below the apex in the direction of the thickness T, which are planar and extend from the support surface 124 and the sealing surface 122 to the apex. Likewise, the engaging surface 126 of the second end block 112B is concave in the width direction so that the deepest part of the concave shape in the width W direction is positioned approximately in the middle of the thickness T of the first end block 112A. The engaging surface 116 of the second end block 112B has portions positioned above and below in the direction of the thickness T of the deepest part of the concave shape in the direction of the width W, which are planar and extend from the bearing surface 124 and the sealing surface 122 to the deepest part the concave shape. The convex and concave shaped engaging surfaces 126 of the end blocks 112A, 112B allow the end blocks 112A, 112B to remain in contact with offsets (e.g., in the thickness direction) of the surfaces of the seal recess in which the seal 110 is used. Thus, the convex and concave shaped engagement surfaces 126 of the end blocks 112A, 112B can prevent increases in leakage past or through the seal 10 under seal recess offset conditions, as discussed above.
    As is also shown in FIGS. 7 to 13, the end blocks 112A, 112B also differ from the end blocks 12A, 12B in that they have the flutes 40 open to the interior of the length L of the end blocks 112A, 112B on the bearing surfaces 124 do not have, in which parts of the ceramic fibers 114 and / or the metallic insert 116 are positioned. Instead, the end blocks 112A, 112B each have or define a countersunk surface, side, or portion 156 countersunk along the direction of length L from the outboard or outer surfaces 132 that are the length L of the Define end blocks 112A, 112B (ie, define the boundary of seal 10 in the direction of length L). The end blocks 112A, 112B each include or define a step surface, side, or portion 158 that extends from the recessed surface 156 to the exterior surface 132 of the end blocks 112A, 112B. In some embodiments, the step surface 158 and / or the countersunk surface are substantially planar. In some embodiments, the recessed surface 156 has at least a portion that is positioned farther from the corresponding outer surface 132 than the portion of the recessed surface 156 that is positioned on or adjacent to the support surface 124. In some embodiments, the countersunk surface 156 is positioned and / or oriented to be countersunk by an amount or a distance in the direction of length L from the outer surface 132 of the end blocks 112A, 112B as large as that Thickness of the metallic shim 16 or greater (and / or the step surface 158 extends from the outer surface 132 of the end blocks 112A, 112B a distance in the direction of the length L to the countersunk surface 156 which is as great as the thickness of the metallic shim 116 or greater). As shown in FIGS. 7 and 11, the countersunk surface 156 and the stepped surface 158 can cooperate and form a recess that receives at least a second tab portion 152 of the metallic shim 116. The at least one second tab portion 152 of the metallic insert 116 can extend from the sealing part 146 and run over the outer edge of the ceramic fibers 114 or over it and over or along the recessed surface 156. Thus, the countersunk surfaces 156 of the end blocks 112A, 112B and the at least one second tab portion 152 of the metallic shim 116 can substantially attach or couple the metallic shim 116, the ceramic fibers 114, and the end blocks 112A, 112B along the direction of the length L. As described above with reference to the tabs 50, the at least one second tab portion 152 can be deformed or oriented in a heated state of the metallic insert 116 such that it exerts a compressive force in a neutral state (i.e. at ambient temperature) of the metallic insert 116.
    The parts of the end blocks 112A, 112B near the lateral outer sides or outer side surfaces 138 can also be designed with a groove or the like 162, which is designed for engagement with the tabs 151 of the metallic shim 116. As shown in Figures 7-10 and 12A-13, the end blocks 112A, 112B may include or define a countersunk side surface, rim, or portion 161 positioned adjacent the support surface 124 and is countersunk along the direction of width W from the outer lateral sides or side surfaces 138 defining the width W of the end blocks 112A, 112B (eg positioned inwardly in the direction of width W with respect to the outer lateral sides or side surfaces 138). The recessed side surface 161 may extend to a second step surface, side, or portion 164 of the end blocks 112A, 112B that extends from the recessed side surface 161 and to the lateral side or side surface 138 of the end blocks 112A, 112B extends. In some embodiments, the second step surface 164 can be planar and / or essentially parallel to the support surface 124 and / or the sealing surface 122. In some embodiments, at least a portion of the recessed side surface 161 that is adjacent to the bearing surface 124 of the end blocks 112A, 112B may be positioned and / or oriented to be an amount or a distance in the direction of width W from the lateral side or Side surface 138 of the end blocks 112A, 112B is countersunk, which or which is as large as the thickness of the metallic shim 116 or greater.
    The recessed side surfaces 161 may comprise or define at least a part which extends or is positioned in the direction of the width W further to the interior of the respective end block 112A, 112B than the part of the recessed side surface 161 which adjoins the support surface 124 of end blocks 112A, 112B are contiguous as shown in Figures 12A and 12B. Thus, the recessed side surface 161 and / or the recessed side surface 161 and the second step surface 164 can form the groove, the recess, the groove or the other concave shape or space 164 which extends in the direction of the Width W extends into the interior of the respective end block 112A, 112B.
    The grooves 164 may be configured to receive at least one tab 151 of the metallic shim 116 therein, as shown in FIG. 7. When the seal 110 is assembled with the ceramic fibers 114 and the metallic shim 116, the at least one tab 151 of the metallic shim 116 can extend from the sealing part 146 and over the outer lateral edges of the ceramic fibers 114 or over them and over or along the recessed side surfaces 161 of the end blocks 112A, 112B and thereby into the side grooves 164 of the end blocks 112A, 112B. Thus, the recessed side surfaces 161 of the end blocks 112A, 112B and the tabs 151 of the metallic shim 116 can substantially fasten or couple the metallic shim 116, the ceramic fibers 114, and the end blocks 112A, 112B along the width W direction. The tabs 151 of the metallic insert 116 can also extend into the grooves 164 in the direction of the width W such that the recessed side surfaces 161 of the end blocks 112A, 112B and the tabs 151 of the metallic insert 116 the metallic insert 116, the ceramic fibers 114 and can attach or couple the end blocks 112A, 112B along the direction of thickness T substantially. As described above, the tabs 151 of the metallic insert 116 can be deformed or oriented in a heated state of the metallic insert 116 so that they exert a compressive force when the metallic insert 116 is in a neutral state. As shown in FIG. 7, the metallic shim 110 may have or define a single tab 151 on each lateral side thereof rather than multiple separate spaced tabs 50 of the seal described above.
    The sealing arrangements disclosed herein result in a low leakage rate similar to that which is possible with traditional recess seals, such as solid metal washer seals, while when applied to modern high temperature turbo machines (e.g. turbo machines with CMC components) the problems of silicide formation, thermal creep and eliminate increased wear and tear. In addition, the seal assemblies disclosed herein may be less prone to manufacturing variance when compared to existing seals. The sealing arrangements disclosed herein therefore reduce leakage with low manufacturing and operational risks and are applicable to both original equipment and retrofit applications.
    Sealing arrangements are provided for reducing leakage between components of turbo-machinery. The seals can include a metallic shim, at least a pair of non-metallic end blocks, and ceramic fibers positioned between the shim and the end blocks. The shim can be mechanically connected to the end blocks so that the metallic shim, the non-metallic end blocks and the ceramic fibers are connected. The end blocks can be designed to accommodate misalignment of turbine components by ensuring sealing engagement of the gasket with the components. The end blocks can be made of a ceramic or glass material and the ceramic fibers can be a high temperature ceramic fiber fabric. The ceramic fibers and / or the end blocks can protect the metallic shim from reaching potentially harmful temperatures during use of the seal, such as use in high temperature turbines with CMC components.
    权利要求:
    Claims (8)
    [1]
    1. A sealing arrangement (10) for positioning in a sealing recess which is at least partially formed by adjacent turbomachine components (142, 144) in order to seal a gap running between the components, the sealing arrangement comprising:a pair of ceramic or glass end blocks (12A, 12B) each having a sealing surface (22, 122) and a bearing surface (24, 124);Ceramic fibers (14) overlying at least a portion of the bearing surfaces of the end blocks; anda metallic shim (16) overlying at least a portion of the ceramic fibers and having a plurality of tabs (151), the plurality of tabs engaging the end blocks to connect the end blocks, the ceramic fibers and the metallic shim.
    [2]
    2. The sealing arrangement (10) according to claim 1, wherein the pair of end blocks (12A, 12B) abuts against engagement surfaces (26, 126) of the end blocks (12 A, 12B) which extend along a longitudinal direction of the end blocks (12 A, 12B) and a thickness direction extending between the sealing surfaces (22, 122) and the bearing surfaces (24, 124) of the end blocks, and wherein the engagement surfaces are configured to permit movement of the end blocks with respect to one another along at least the thickness direction.
    [3]
    3. Sealing arrangement (10) according to any one of the preceding claims, wherein the metallic shim (16) and the ceramic fibers (14) are deformable in order to allow the movement of the end blocks (12 A, 12B) with respect to one another at least along a thickness direction which is extends between the sealing surfaces (22, 122) and the bearing surfaces (24, 124) of the end blocks.
    [4]
    4. The sealing assembly (10) of claim 2, wherein the engagement surface (26, 126) of each of the end blocks has a planar surface extending between the sealing surface (22, 122) and the bearing surface (24, 124) of the respective end block; or wherein the engaging surface of one of the end blocks (12A, 12B) defines a concave shape extending along the width direction and the other of the end blocks defines a convex shape extending along the width direction.
    [5]
    5. Sealing arrangement (10) according to one of the preceding claims, wherein the end blocks each have at least one groove (40) which is designed to receive at least part of the metallic insert (16) in it.
    [6]
    The seal assembly (10) of claim 5, wherein the flutes of each of the end blocks (12A, 12B) are formed on the bearing surface (24, 124) of the end blocks and wherein the plurality of tabs (151) of the metallic shim (16) extend therealong a thickness direction extending between the bearing surface (24, 124) and the sealing surface of the end blocks.
    [7]
    7. The seal assembly (10) of any preceding claim, wherein the plurality of tabs (151) exert a biasing force against the end blocks (12A, 12B) when the seal assembly (10) is at ambient temperature.
    [8]
    8. Turbomachine comprising:a first turbine component (142) and a second turbine component (144) adjacent the first turbine component, the first and second turbine components forming at least a portion of a seal recess that extends across a gap between the turbine components; anda seal assembly (10) positioned within the seal recess of the first and second turbine components and extending across the gap therebetween, the seal assembly comprising: a pair of ceramic or glass end blocks (12A, 12B) each having a sealing surface ( 22, 122) and a support surface (24, 124);Ceramic fibers (14) overlying at least a portion of the bearing surfaces of the end blocks (12A, 12B); anda metallic shim (16) overlying at least a portion of the ceramic fibers and having a plurality of tabs (151), the plurality of tabs engaging the end blocks to connect the end blocks, the ceramic fibers and the metallic shim.
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    同族专利:
    公开号 | 公开日
    JP2016205387A|2016-12-08|
    JP6746362B2|2020-08-26|
    DE102016106200A1|2016-10-27|
    CN106065788B|2021-02-09|
    CH711014A2|2016-10-31|
    CN106065788A|2016-11-02|
    US20160312635A1|2016-10-27|
    US9850772B2|2017-12-26|
    引用文献:
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    US7563504B2|1998-03-27|2009-07-21|Siemens Energy, Inc.|Utilization of discontinuous fibers for improving properties of high temperature insulation of ceramic matrix composites|
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    法律状态:
    2017-03-15| NV| New agent|Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH |
    2019-05-31| NV| New agent|Representative=s name: FREIGUTPARTNERS IP LAW FIRM DR. ROLF DITTMANN, CH |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/695,288|US9850772B2|2015-04-24|2015-04-24|Seals with a thermal barrier for turbomachinery|
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